Metal aeroplane



A. J. COOK.

METAL AEROPLANE.

APPLICATION man JULY 8. 1920.

1,363,569,, Patented Dec. 28, 1920.

2 SHEETS-SHEET 1.

A. J. COOK.

METAL AEROPLANE.

APPLICATION FILED JULY 8. 1920.

Patented Dec. 2& 1920 2 SHEETSSHEET 2- ADONIRAM J. COOK, OF 'WESTERLO, NEW YORK.

METAL AEROIPLAN E.

Specification of Letters Patent.

Patented Dec. 28, 1920.

Application filed July 8, 1920. Serial No. 394,709.

To all whom it may concern:

Be it known that I, ADONIRAM J. COOK, a citizen of the United States, residing in Westerlo, in the county of Albany and tate of New York, have invented certain new and useful Improvements in Metal Aeroplanes, of which thefollowing is a specification.

The object of this invention is to provide an improved construction in metal aeroplanes, in which the wings are separate and detachable so that the apparatus may be stored in comparatively small space.

A further object is in the manner of constructing and assembling the brace elements whereby a maximum of strength and stability of construction is attained with a minimum of weight.

These and other objects, which will become apparent as the description progresses, are attained by the novel construction, combination and arrangement of parts, hereinafter described and shown in the accompanying drawings, forming a material pait of this disclosure, and in which Figure 1 is a perspective view of a metal aeroplane, partly dismembered, made in accordance with the invention.

Fig. 2 is an enlarged transverse sectional view taken through one of the wings.

Fig. 3 is a further enlarged fragmentary sectional view of the same.

Fig. 4 is a perspective view showing the construction and assembly of the wing elements.

Fig. 5 is an enlarged fragmentary perspective view showing the wing frame structure.

Fig. 6 is a similar View of one of the metal struts employed.

Fig. 7 is a perspective view showing further details of construction.

Referring to the drawings in detail the numeral 15 designates in general the fuselage or body of the aeroplane, the same being of conventional type of construction, provided with a propeller 16 at the front, horizontal and vertical rudders, respectively 17 and 18 at the rear and a cock pit 19, in which the several control devices are accessible to the aviator.

In the. biplane as shown in Fig. 1, the

and 26, and 22 and 28 lower wing section 20 has upon its upper side a platform 21 to which is attached the fuselage 15, the platform extending to engage the mating section 22, by means of bolts or like fastenings passing through the respective openings 23 and 24.

The corresponding upper wing section 26 has a plate 27 directly over the fuselage, to wh ch may be connected the section 28 by slmilar fastening means passing through the openings 29 and 30.

Between the upper and lower sections 20 are a plurality of posts 32 braced by diagonally disposed guy rods 33, it being understood that each section is separate and independent in itself.

It will be noted the elements 21 and 27 are so arranged as to produce a bracin efi'ect making the aeroplane strong and reliable at the middle of the fuselage where strength is most required.

Extending between the platform 21 and plate 27 are channel posts 35 (see Fig. 6) having flanged ends 36 containing openings 37 for rivets by which they are firmly held in assembled position; other openings 38 provide convenient means for bolting or riveting these posts direct to the fuselage 15. (see Fig. 1).

The wing structure,shown in detail in Figs. 2, 3, 4, 5 and 7, constitute an important feature of the invention.

Each is comprised of a plurality of rafters or'ribs' formed of pairs of rolled angles, generally indicated by the characters 40 and 40', spaced and positioned as best shown in These ribs are bent to the shape shown in Fig. 2, the vertical elements being notched, as at 41, to permit bending, forming a bowed front end 42 from which the slightly convex bottom 43 extends rearwardly, the upper elements 44 presenting a convex surface, gradually approaching the lower element toward the rear end. while secured between them is the filler rail 45.

These several ribs are reinforced and maintained in shape by angularly disposed struts 46 secured between the spaced vertical elements of the rib angles in parallel planes, while at suitable points, near the front and rear, the ribs are connected in spaced relation by plates 48 bent to form tenons 49 disposed between the angles and extending the full length of each wing element. a

To the adjacent sides of the plates are attached paired angles 50 having between them transversely disposed diagonal struts 51, the entire structure being securely riveted as indicated and forming a firm rigid frame connected by the posts 32, into biplane wings of stability and lightness.

The metal cover plates 52 are held to the frames in the manner shown in Fig. 5, the edges of the plates being pressed into the space between the angles and 41, by tenons 53 formed with plates 54, secured to the horizontal elements of the angles by screws 55. A U shaped metal strip 56, suited to the rib ends 42, supports the plates, this forming impervious joints, which, if desired, 'may be readily broken for the removal or replacement of the plate portion of the wings.

From the foregoing it will be seen that the wing elements may be readily detached from the floor or platform 21 and roof plate 27, permitting the entire structure to be stored in a limited space, and that the structure of the wings is such as to attain the objects sought.

Having thus described my invention, what I claim as new and desire to secure by Letters Patent, is

1. An aeroplane wing comprising pairs of rolled angles bent reentrantly, their limbs being arranged respectively adjacent and laterally, plates overlying the lateral limbs, tenons formed with said plates, said tenons 'extending inward between the adjacent limbs, lattice elements extending between opposed limbs from one section to the other and cover plates engaging between the tenoned plates and walls of adjacent angles whereby they are held in tension.

2. An aeroplane wing comprising pairs of rolled angles bent reentrantly to present substantially parallel upper and lower frame elements, lattice bars connecting between said elements, thin metal cover plates arranged in overlapping relation over said angles and tenoned cover plates secured to said angles, their tenons forcing the overlapping edges of said cover plates between the inner sides of said pairs of angles against the ends of said lattice bars.

3. An aeroplane wing comprising pairs of rolled angles bent reentrantly to present substantially parallel upper and lower frame elements, lattice bars connecting between said elements, transverse angles connecting between adjacent pairs of the rib angles, metal strips interposed at the joints therebetween, said strips being bent at their centers tightly upon themselves and entered between said pairs of angles, plate coverings extending over said rib angles and means for rigidly engaging the overlapping edges of said plate covering between the angles.

4. An aeroplane wing comprising a plurality of ribs formed of pairs of rolled angles and bent upon themselves, lattice connections between the upper and lower rib elements held between the angles, lattice beams connecting said ribs in spaced relation, a rail at the rear of the ribs, a rolled element at the front, metal cover plates disposed over said ribs, rail and rolled elements, and means engaging between the angles for holding the plates in position.

5. An aeroplane wing comprising a plurality of ribs formed of pairs of rolled angles and bent upon themselves, transverse beams composed of angles and lattice elements engaging said ribs whereby they are held in rigid spaced relation, connections at the ends of said ribs, plate strips having tenons adapted to enter between each pair of rib angles clamping coverings therebetween, and means for engaging said strips to said angles whereby the covering is held taut along its lateral edges.

In testimony whereof I have signed my name to this application.

ADONIRAM J. COOK. 

